Title : DEVELOPMENT OF A SUPERSONIC TRANSPORT AIRCRAFT ENGINE. PHASE II- C.

Descriptive Note : Monthly progress rept. no. 11, 1-31 May 66.

Corporate Author : PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FLA FLORIDA RESEARCH AND DEVELOPMENT CENTER

Report Date : 10 JUN 1966

Pagination or Media Count : 157

Abstract : The second build of engine FX-161 was completed and delivered to test on 14 May. Testing was terminated on 20 May, after 2.08 hours (total time 13.76 hours) because of over-temperature indications from the instrumented 1st-stage turbine vanes and evidence of distress of the transition duct. Several burned areas in the transition duct were found during disassembly inspection. This problem has been attributed to the airflow out of the individual starting bleed valves, which caused (1) disturbance of the air in the annulus outside the combustor, thereby locally reducing the cooling air to the transition duct; and (2) hot spots on the transition duct due to locally higher fuel/air ratios. The third build of engine FX-161 and the first build of engine FX-162 are being modified to utilize the diffuser bleed manifold for high compressor bleed. Both engines are scheduled to be mounted for test in mid-June. The rebuild of the high compressor rig using recambered stators showed a slight improvement of the high speed surge pressure ratio.